Airplane



Aug. 7, E923.

H. A. ZETTEL AIRP-LANE Filed Nov. 18 1919 4 Sheecs-Sheel l 7, H9235, gl

H. A. ENEL AIRPLANE Filed Nov. 18, 1919 4 SheeiS-Sheet 2 HEBT ZETTEL, @F3T. PAUL, MEWESUTA.

. meeneem.

Application med! iovemler w, wie. Serial fo. 51133,@38.

To ali whom t may cowern:

Be it known that HERBERT A. ZETI'EL, a oitizen'of the United States,residing at St. Paul, in the county of Ramsey and State 5 of Minnesota,have invented e new and usefui Improvement in Airplanes, of which theolowing is a specification.

The primary object of the invention is the provision of an aircraftadapted foi' propui- E@ sion et points free from the siii' inerferenceoiiered by di'erent poieions of ehe oiei'; whereby meximum efeienoy' isobtained combined with niceey oonrei dui'ieg Eight. y f

A. furthe? object oi ehe inyeiieion is the provision o' pi'opeiiimgmeans foi eioi'e, :mtometioaiiy oonroiied with ee-thei'ing biedes endmenuaiiy edjusebie for @comme steering purposes', the eomroiiiiig meansoeing such that substeneieiiy "veicei oi* ae cents ai Sheep angiee isieediiy eocompisiied. A stili uiher objec of ehe invention is theprovision of e propeiee driven tied seefed aeroplane whereby eine pilot35 cause the craft fo ti'eve in any' desired diieotion by easiiyshifting the propelers simultaneously with the automatic, featheringz ofthe pi'opeiier blades during opeetion.

With zhese general objects in View, the iiiyeni-ion consists of thenevel combination end eiiengement o peints eereioeee mole uiiy describedviin commotion Weth the eeoompeiiying di'ewings, and 'eben eieimed.

im the dmeiiigs forming e, pmt of ehi@ epi piieeeion iixe referenceeheeeoers deeigneite L ooeieepomding parte thiougiou @he vseyeiei viewe,and

Figure i is e front eieveioo o ie eieb, Figure 2 is e side View idioeopeiceieiiy iii-okee away,

Figure 3 is e rear eievetione View of 'the seme broken ewey,

Figee is e' iop pien View of the erelid; with parte broken away.

Figure 5 is e. deteii View of Ehe piemeey steering gems,

Figure 6 ie e. diagiemmetie View of the cycle of opeeetion @fiilepropeiliee iiiedee end Figure Y ie e ,geometric development of ehe csirocomzoi'for the featiei'img biedes.

My eefropiene comibi'xes heicopte end eerodymimie principles keinecommented for upward es Well as forward Hight it being understood thate, body suspended in air loses am amount of weight equei to the pessueof air conveyed from above to e points below the body causing1 thepartiel vacuum Ethereabove for exerting e. lifting power es weil asutiiizing the increased ein pfessuie below the body.

iin cari/ying out che principles/of my inveneion i have iiustieted oneemoodimem of aiioree edepied for iiis purpose end consisting o? e.'fuselage i9, en empennege il, e Chassis ivi-y aircrew-fi. iai zie om ofe, iii-piene with e ioweirL "sensvei'se piene 137 meumeed upon 'diefue.-

i0 with mi upper @ieee 11i. posiiiened iieeaboye, seid 7@ bee-weee -oepianos et eine opposite A bevreen ehe eeifooiis oi' iiting ple-nes i3and i4 with iege 22 secured eo the iowee piene 13, above iie ueeiege U.direct drive o siieped piopeiier im'bs 23 outwrdig of the emes 2O .isprovided by keying o?? otherwise seeming. 4die hubs 23 upon 'eineopposite oiiei ende of eide creek eiieze 2li, of he moor 2l. Tubuieimembers or eieeves 2:5 are joeimied upon the oppoeire eind poirione Jeeshefe 24;-, eeeii of' seid. sieeves having e. depeeding'evei: 26 wzh ebfurceted lower eed 2T? poeioned ai'. opa oosie sides o?? *the motor 'fwiiie oem deems 28 me attac-eed io die ieee ende of? ziie sieeves 25 andjouneed in enti-*esiom bee-ringe 29 ceereiiy of iie frames 2o. Thepropeers being ewofbieded, eine biedee 3G rhereo have joureeie Si.i'oetebiy momifced upon axles 32 opposizey projeoting from Mee hues 23Whexeey the niedes 3G revolve Wih oe inubs 23 cepeeie of. i'iependen;miie? oeeion upon iiie efzziee 82. Rieke 33 peoted to inge 34C upon eineioumee 3i 'wife the inner ends of the iinke imving "bell memiiers B,eideeie im eem moves 3%' geroemd h@ dname 95 @ming @he eofime',

rotation of the hubs 23 by the motor 21, the links 33 will cause theblades 30 to automatically fea-ther during their recovery stroke itbeing understood that the forward downward movements of the bladesconstitutes the power stroke regulated in the manner hereinafterdescribed for exerting different degrees of lifting and forward drivingpower to the craft. The blades 3() are designed for positioning at anangle to the frames 20 during their propelling movements or in otherwords, the lateral dimension of each blade 30, will project upwardly andoutwardly from the plane of the adjacent frame 2O during the downwardpower stroke ofthe blade.

This manner of operation serves to draw the air downwardly from thesloping upper aerofoil 14 and forcing the air beneath the concaved loweraerofoil 13. The formation of a partial vacuum above the planes drawsthe craft upwardly assisted by the upward pressure of, the air forciblycirculated to a point beneath the lower plane 13 at opposite sides ofthe fuselage 10. A U-shaped yoke 37 swings upon the motor shaft 24beneath the motor and between the legs 22 -while an operating shaft 38for the levers 26 is positioned within the bifurcated ends 27 of thelevers 26 beneath the yoke 37. A steering post 39 centrally depends froma thrust bearing 40 carriedby the yoke 37, the said post axiallyextending through a gear casing 41 centrally carried by the shaft 38. Apinion-42 upon the shaft 39 meshes with the pinions 43 within the casing41 while the pinions 43 in turn mesh within the gear 44 of said casingthereby forming a dille'rential construction whereby the shaft 38 islaterally turned in an opposite direction from the direction of rotationof said shaft 39.

A. steering wheel 45 upon the lower end of the shaft 39 is readilyaccessible from the drivers seat 46 within the 1uselare 1() while atransparent panel or window 47 in the forward nose or bow portion 43 of'the fuselage permits the pilot free visual access forwardly of the craftwhile side openings or windows 49 may be provided of any form in saidfuselage 10. The feathering action of the two blades 30 of eachpropeller occur at uniform points in the path of rotation ot the bladesand under normal conditions the two propellers feather simultaneously sothat their power and recovery strokes occur together for beatingdownwardly and rearwardly Vthrough the air. This uniform featheringoperation of the blades of the two propellers is shifted to differentpoint-s of rotation by oscillatirre the post 39 upon the' longitudinalaxis of the fuselage 10.

This is accomplished by shifting the yoke 3?, shaft 38 and levers 26upon the swinging` movement of the post, 39, the movement ot 23partially rotating the vsleeves 25 and drums 28 and the shifting ofthecam slots 36 changes the timing of the partial rotation of the bladejournals 31 upon the axles 32 and regulates the position of the powerstroke of the propeller blades. The power stroke of the blades 30 occursin their path of travel through the arc AB, Figure 6, when the power isprimarily designed for upward movement of the aircraft and upon the arcBC when forward propelling` power is primarily desired.

The travel of the propeller blade 30 through the are iB however exerts acompound lift and pull, the pulling action occurring through-the thirdarc BC as shown in Figure 6.

The steering operation accomplished by the post 39 turned bythe wheel45, is effected by shifting the cam drums 28 in opposite directions andvwhereby the blades 30 of the propeller at one side ofthe craft will beshift-ed for exerting greater lifting or pulla left hand turn of thewheel 45 steers the craft toward the left. The complete control is hadthrough the wheel 45 for oscillating' the post 39 to change the timingof the propellers for simultaneously7 lifting or pulling operation andalso for oppositely shifting the blades oi the two propellers to steerthe craft through any desired maneuvers iu aerial travel. By this simpleconstruction` the propellers being outwardly of the sides of the craft,are free from all air interference and their position for operation asset. forth causes the craft to rise at sharp angles into the air'and Vtotravel therethrough at will under the accurate control of the steeringmechanism etlected and made possible by the controlled operation ot thecam drums 28.

While the form of the invention herein set forth is believed preferableit will be understood that various changes may be made therein withoutdeparting from the spirit and scope of the invention as claimed, itbeing understood that a plurality of propellers can be used upon eachside ot the craft if found desirable.

What I claim as new and desire to secure by Letters Patent is 1. An aircraft comprising a longitudinal trame work, a transverse aerofoilmounted on said frame work and extending outwardly beyond the same onthe sides there of. said aerofoil inclining laterally from the centerpoint thereof to the outer ends, and vertically rerolnble propellerspositioned outwardly oil the lowerinost ends of the nasser? aerotoiladapted for exhausting the air above the aerofoil during the upwardmovement of the craft.

.2. An air craft comprising a longitudinal frame work, a transverseaerofoil mounted on said frame work and extending outwardly beyond thesame'on the sides thereof, said aerofoil inclin'ing laterally lfromthe`center point thereof vto the outer ends, and verticall revolublepropellers positioned outwardly of the lowermost ends of the aerofoiladapted for exhausting the air above the aerofoil during the upwardmoven ment of the craft, said propellers being adapted for f gcingl theair beneath the aerofoil 4wh'ereby upward pressure is exerted on thecraft.

3. An aircraft comprising a fuselage, upper and lower planestransversely carried thereby with the end portions of the planesdownwardly inclined from the central ridge thereof, upright framesconnected between the outer ends of the planes, bladed propellersmounted for rotation in a vertical plane at the outer end of said framesand adjusting cams for the blades of said propellers jdurnaled in saidframes.

4. An aircraft comprising a fuselage, upper and lower planestransversely carried thereby with the end portions of the planesdownwardly inclined from the central ridge thereof, upright framesconnected between the outer ends ofthe planes, bladed propellers mountedfor rotation outwardly of said frames, adjusting cams for the blades ofsaid propellers journaled in said frames,

a motor between said planes having its shaftV projectin through theframes and cams o erative y connected to said propellers, s eevesjournaled upon said shaft at opposite sides of the motor and secured tosaid cams and shifting means for the sleeves.

5. An aircraft comprising ajuselage, upper and lower planes transverselycarried Vthereby with the end ortions' ot the planes downwardly inclinedrom the central ridge thereof, upright frames 'connected between theouter ends of the planes, bladed pro pellers mounted for rotationoutwardly or said frames, adjusting cams for the blades of saidpropellers journaled in said frames, a motor between said planes havingits shaft projecting through the frames and, cams operatively connectedto said pio pellers, sleeves journaled upon said sha-it.

at opposite sides of the motor,I and secured to. said cams, adjustinglevers depending from the adjacent inner ends of the sieeves and meansadapted for oscillating sa2 levers in the same or opposite direction lnaircraft comprising averse planes mounted ther. een the ends et theplanes, the eater end el a propeller mounted for revolution outwardly ofeach drum including axially journaled blades, and operative connectionsbetween said propeller blades and drums whereby the blades of the twopropellers are adapted and operate in a vertical plane and toautomatically feather simultaneously.

7. An aircraft comprising a fuselage, transverse planes mounted thereon,frames between the ends ofthe planes, a cam drum journaled in eachframe, a4 propeller mount-` ed for revolution outwardl of each drumincluding axially journale blades, operative connections between 'said,propeller blades and drums whereby the blades of the two propellers areadapted to automatically feather simultaneously, and means for manuallyadjusting the drums simultaneously whereby the feathering of the bladesis timed at dierent points inthe plane of revolution.

8. An aircraft comprising a fuselage7 different points in the plane ofrevolution,

and means associated with the drum-adjusting means whereby the drums areadapted for shifting in opposite directionsrduring the steeringoperation of the craft during flight. 9. An aircraft comprising afuselage, up per and lower transverse planes carried thereby, framesbetween the ends of the planes, a. motor centrally between the planes,cam drums journaled in said frames, a power shaft for the motorjournaled through said drums, propeller hubssecured to the free ends ofsaid shaft outwardly of the drums, opposite blades journaled upon saidhubs and operative eonnections between the blades of each heb and theadjacently positioned drum wherein' the blades are adapted for partialrotation relatively of the hub during t comprising a fuselage, upand l.erse planes carried thereby., frames between the ends of the planes, anoter centrally between the planes, d.' nis ','enrnaled in said trames,a power eter jiournaled through said its secured to the tree o thedrums, ionrualed vupon said hubs, s between the blades et aeentlypositioned drum ted for partial l ,h dering lUG tion of the shaft, andshifting means for the drums adapted for operation within the fuselagewhereby the drums may be partially rotated in the same or differentdirections at will.

11. An aircraft comprising a fuselage, upper and lower transverse planescarried thereby, frames between the ends of the planes, a motorcentrally between the planes, cam drums journaled in said frames, apower shaft for the motor journaled through said drums, propeller hubssecured tothe free end-s of said shaft outwardly of the drums, oppositeblades journaled upon said hubs, operative connections between theblades of each hub and the adj acently positioned drum wherebyl theblades are adapted for partial rotation relatively of thehub duringrotation of the shaft, a yoke journaled upon the motor shaft dependingbeneath the motor, a steering post swiveled to the yoke depending intothe fuselage and operative conneo tions between 'said post and drumswhereby the drums are adapted for simultaneous Shifting duringoscillations of the post.

1Q. An aircraft comprising a fuselage, upper and lower transverse planescarried thereby, frames between the ends of the planes, a motorcentrally between the planes, cam drums journaled in said frames, apower shaft for the motor journaled through said drums, propeller hubs.secured 'to the free ends of said shaft outwardly of the drums,opposite blades journaled upon said hubs, operative connections bet-Weenthe blades of each hub and the adj acently positioned drum whereby theblades are adapted for partial rotation relatively of the hub duringrotation of the shaft, a yoke journaled upon the motor shaft dependingbeneath the motor, a steering post4 swiveled to the yoke depending intothe fuselage, sleeves secured to the drums journaled upon 4the motorshaft, operating levers depending from said sleeves at opposite sides ofthe motor and operative connections between said post and levers wherebythe levers are adapted for swinging in the same or opposite directionsat will.

13. An aircraft comprising a fuselage, upper and lower transverse planescarried thereby, frames between the ends of the planes, a motorcentrally between the planes, cam drums journaled 'rin said frames, apower shaft ,for the motor journaled through said drums, propeller hubssecured to the free ends of said shaft outwardly of the drums, oppositeblades journaled upon said hubs, operative connections between theblades of each hub, and the adjaoently positioned drum whereby theblades are adapted for partialv rotation relatively of the hub duringlrotation of the shaft, a yoke journaled upon the motor shaft dependingbeneath the motor, a steering post swiveled to the yoke depending intothe fuselage, sleeves secured to the drums journaled upon the motorshaft, operating levers depending from said sleeves at opposite sides ofthe .niotor, a shaft beneath the yoke loosely connected tothe free endsof said levers, a dif!- ferential casing centrally of said lever shaftthrough which said post is journaled and differential gear connectionsbetween said post and casing whereby the partial rotation of the post isadapted for shifting said levershaft in an opposite direction during thead justment of the propeller blades in the Steering of the craft.

HERBERT A. ZETTEL.

